EPPLER 330 AIRFOIL (e330-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 330 AIRFOIL (e330-il) Reynolds number: 100,000 Max Cl/Cd: 40.61 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e330-il-100000.txt Download as CSV file: xf-e330-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 330 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5351 0.09515 0.09082 0.0023 1.0000 0.0812
-8.500 -0.5528 0.09080 0.08650 -0.0025 1.0000 0.0824
-8.250 -0.5761 0.08807 0.08372 -0.0034 1.0000 0.0831
-8.000 -0.5999 0.08637 0.08183 -0.0030 1.0000 0.0837
-7.750 -0.5795 0.07919 0.07487 -0.0030 1.0000 0.0860
-7.500 -0.5683 0.07567 0.07141 -0.0020 1.0000 0.0891
-7.250 -0.5685 0.07244 0.06814 -0.0015 1.0000 0.0929
-7.000 -0.5951 0.07286 0.06794 0.0007 1.0000 0.0981
-6.750 -0.5734 0.06542 0.06090 0.0002 1.0000 0.1012
-6.500 -0.5632 0.06234 0.05783 0.0012 1.0000 0.1058
-6.250 -0.5661 0.05970 0.05488 0.0030 1.0000 0.1138
-6.000 -0.5514 0.05621 0.05150 0.0041 1.0000 0.1198
-5.750 -0.5454 0.05331 0.04848 0.0058 1.0000 0.1298
-5.500 -0.5370 0.05061 0.04571 0.0076 1.0000 0.1435
-5.250 -0.5283 0.04803 0.04308 0.0095 1.0000 0.1570
-5.000 -0.5204 0.04565 0.04072 0.0117 1.0000 0.1738
-4.750 -0.5247 0.04401 0.03915 0.0154 1.0000 0.1873
-4.500 -0.4912 0.04154 0.03647 0.0122 0.9720 0.2331
-4.250 -0.4185 0.03263 0.02549 0.0114 0.9519 0.0727
-4.000 -0.3666 0.02901 0.02102 0.0097 0.9276 0.0556
-3.750 -0.3254 0.02579 0.01744 0.0083 0.8991 0.0528
-3.500 -0.2917 0.02374 0.01501 0.0087 0.8699 0.0520
-3.250 -0.2617 0.02223 0.01319 0.0098 0.8425 0.0536
-3.000 -0.2337 0.02101 0.01177 0.0108 0.8172 0.0578
-2.750 0.0295 0.01750 0.01121 -0.0230 0.7865 1.0000
-2.500 0.0499 0.01741 0.01080 -0.0219 0.7609 1.0000
-2.250 0.0695 0.01736 0.01043 -0.0205 0.7396 1.0000
-2.000 0.0901 0.01731 0.01011 -0.0194 0.7195 1.0000
-1.750 0.1111 0.01727 0.00984 -0.0184 0.7011 1.0000
-1.500 0.1328 0.01726 0.00960 -0.0175 0.6845 1.0000
-1.250 0.1550 0.01726 0.00938 -0.0166 0.6692 1.0000
-1.000 0.1771 0.01728 0.00921 -0.0158 0.6545 1.0000
-0.750 0.1996 0.01732 0.00908 -0.0150 0.6409 1.0000
-0.500 0.2222 0.01737 0.00899 -0.0142 0.6280 1.0000
-0.250 0.2450 0.01745 0.00891 -0.0135 0.6158 1.0000
0.000 0.2677 0.01753 0.00884 -0.0126 0.6049 1.0000
0.250 0.2909 0.01763 0.00882 -0.0119 0.5934 1.0000
0.500 0.3144 0.01775 0.00888 -0.0114 0.5821 1.0000
0.750 0.3378 0.01789 0.00892 -0.0108 0.5719 1.0000
1.000 0.3609 0.01803 0.00893 -0.0100 0.5629 1.0000
1.250 0.3848 0.01820 0.00910 -0.0095 0.5523 1.0000
1.500 0.4084 0.01839 0.00924 -0.0089 0.5432 1.0000
1.750 0.4319 0.01857 0.00933 -0.0082 0.5346 1.0000
2.000 0.4558 0.01881 0.00960 -0.0078 0.5252 1.0000
2.250 0.4792 0.01901 0.00968 -0.0070 0.5180 1.0000
2.500 0.5032 0.01928 0.01004 -0.0066 0.5083 1.0000
2.750 0.5269 0.01954 0.01027 -0.0060 0.5007 1.0000
3.000 0.5506 0.01980 0.01054 -0.0054 0.4921 1.0000
3.250 0.5742 0.02013 0.01090 -0.0050 0.4841 1.0000
3.500 0.5978 0.02038 0.01112 -0.0043 0.4765 1.0000
3.750 0.6213 0.02078 0.01165 -0.0038 0.4682 1.0000
4.000 0.6448 0.02101 0.01184 -0.0030 0.4612 1.0000
4.250 0.6680 0.02147 0.01243 -0.0026 0.4524 1.0000
4.500 0.6915 0.02170 0.01263 -0.0018 0.4460 1.0000
4.750 0.7142 0.02222 0.01333 -0.0013 0.4368 1.0000
5.000 0.7377 0.02245 0.01348 -0.0004 0.4306 1.0000
5.250 0.7596 0.02299 0.01424 0.0001 0.4211 1.0000
5.500 0.7823 0.02336 0.01466 0.0009 0.4139 1.0000
5.750 0.8044 0.02378 0.01520 0.0017 0.4053 1.0000
6.000 0.8262 0.02428 0.01581 0.0025 0.3971 1.0000
6.250 0.8488 0.02451 0.01607 0.0035 0.3892 1.0000
6.500 0.8694 0.02513 0.01692 0.0043 0.3799 1.0000
6.750 0.8932 0.02516 0.01685 0.0054 0.3729 1.0000
7.000 0.9125 0.02577 0.01772 0.0064 0.3623 1.0000
7.250 0.9330 0.02619 0.01827 0.0075 0.3529 1.0000
7.500 0.9567 0.02613 0.01813 0.0086 0.3446 1.0000
7.750 0.9753 0.02660 0.01886 0.0098 0.3333 1.0000
8.000 0.9947 0.02698 0.01939 0.0111 0.3225 1.0000
8.250 1.0158 0.02705 0.01951 0.0123 0.3122 1.0000
8.500 1.0387 0.02688 0.01927 0.0135 0.3015 1.0000
8.750 1.0563 0.02713 0.01970 0.0151 0.2887 1.0000
9.000 1.0742 0.02726 0.01995 0.0167 0.2754 1.0000
9.250 1.0917 0.02739 0.02021 0.0183 0.2616 1.0000
9.500 1.1084 0.02750 0.02038 0.0200 0.2470 1.0000
9.750 1.1242 0.02768 0.02056 0.0219 0.2317 1.0000
10.000 1.1341 0.02825 0.02130 0.0243 0.2149 1.0000
10.250 1.1428 0.02891 0.02206 0.0268 0.1981 1.0000
10.500 1.1492 0.02968 0.02285 0.0295 0.1815 1.0000
10.750 1.1527 0.03066 0.02380 0.0325 0.1660 1.0000
11.000 1.1531 0.03188 0.02501 0.0357 0.1524 1.0000
11.250 1.1495 0.03326 0.02642 0.0394 0.1403 1.0000
11.500 1.1427 0.03476 0.02800 0.0432 0.1301 1.0000
11.750 1.1352 0.03620 0.02937 0.0472 0.1219 1.0000
12.000 1.1218 0.03769 0.03094 0.0514 0.1156 1.0000
12.250 1.1141 0.03953 0.03274 0.0542 0.1087 1.0000
12.500 1.1041 0.04162 0.03490 0.0564 0.1023 1.0000
12.750 1.0989 0.04391 0.03720 0.0579 0.0961 1.0000
13.000 1.0913 0.04647 0.03986 0.0590 0.0906 1.0000
13.250 1.0904 0.04889 0.04224 0.0600 0.0846 1.0000
13.500 1.0784 0.05218 0.04575 0.0600 0.0808 1.0000
13.750 1.0869 0.05417 0.04753 0.0613 0.0740 1.0000
14.000 1.0710 0.05817 0.05183 0.0607 0.0719 1.0000
14.250 1.0590 0.06220 0.05608 0.0599 0.0699 1.0000
14.500 1.0476 0.06629 0.06034 0.0589 0.0676 1.0000
14.750 1.0529 0.06871 0.06261 0.0596 0.0622 1.0000
15.000 1.0347 0.07378 0.06791 0.0575 0.0616 1.0000
15.250 1.0132 0.07972 0.07409 0.0549 0.0612 1.0000
15.500 0.9900 0.08612 0.08068 0.0516 0.0611 1.0000
15.750 0.9655 0.09332 0.08805 0.0479 0.0615 1.0000
16.000 0.9397 0.10132 0.09619 0.0438 0.0622 1.0000
16.250 0.9113 0.11032 0.10529 0.0391 0.0628 1.0000
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Polar data table (+)
Polar graphs
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